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On the flow of a compressible fluid by the hodography method I : unification and extension of present-day results

On the flow of a compressible fluid by the hodography method I : unification and extension of present-day results

Date: March 1, 1944
Creator: Kaplan, Carl
Description: None
Contributing Partner: UNT Libraries Government Documents Department
On the flow of a compressible fluid by the hodography method II : fundamental set of particular flow solutions of the Chaplygin differential equation

On the flow of a compressible fluid by the hodography method II : fundamental set of particular flow solutions of the Chaplygin differential equation

Date: November 1, 1944
Creator: Kaplan, Carl
Description: None
Contributing Partner: UNT Libraries Government Documents Department
On the Flutter of Cylindrical Shells and Panels Moving in a Flow of Gas

On the Flutter of Cylindrical Shells and Panels Moving in a Flow of Gas

Date: September 1, 1958
Creator: Stepanov, R. D.
Description: The equations of shells are taken in the form of the general technical theory of shallow shells and shells of medium length. The aerodynamic forces acting on a shell are taken into account only as forces of excess pressure according to the formula proposed by A.A. Iliushin in reference 3.
Contributing Partner: UNT Libraries Government Documents Department
On the flying qualities of helicopters

On the flying qualities of helicopters

Date: January 27, 1949
Creator: Reeder, John P & Gustafson, F B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
On the form of the turbulent skin-friction law and its extension to compressible flows

On the form of the turbulent skin-friction law and its extension to compressible flows

Date: May 1, 1952
Creator: Donaldson, Coleman Dup
Description: None
Contributing Partner: UNT Libraries Government Documents Department
On the Formation of Shock Waves in Subsonic Flows With Local Supersonic Velocities

On the Formation of Shock Waves in Subsonic Flows With Local Supersonic Velocities

Date: April 1, 1950
Creator: Frankl, F. I.
Description: In the flow about a body with large subsonic velocity if the velocity of the approaching flow is sufficiently large, regions of local supersonic velocities are formed about the body. It is known from experiment that these regions downstream of the flow are always bounded by shock waves; a continuous transition of the supersonic velocity to the subsonic under the conditions indicated has never been observed. A similar phenomenon occurs in pipes. If at two cross sections of the pipe the velocity is subsonic and between these sections regions of local supersonic velocity are formed without completely occupying a single cross section, these regions are always bounded by shock waves.
Contributing Partner: UNT Libraries Government Documents Department
On the gas dynamics of a rotating impeller

On the gas dynamics of a rotating impeller

Date: March 1, 1956
Creator: Busemann, Adolf
Description: It is shown that for a compressible flow with constant entropy the pressure rise maintains the direct relation to the circulation around the blades existing for incompressible flow. In contrast, however, the torque, and with it the power consumption, is increased because of sound waves traveling to infinity already at subsonic circumferential speeds.
Contributing Partner: UNT Libraries Government Documents Department
On the general theory of thin airfoils for nonuniform motion

On the general theory of thin airfoils for nonuniform motion

Date: January 1, 1944
Creator: Reissner, Eric
Description: General thin-airfoil theory for a compressible fluid is formulated as boundary problem for the velocity potential, without recourse to the theory of vortex motion. On the basis of this formulation the integral equation of lifting-surface theory for an incompressible fluid is derived with the chordwise component of the fluid velocity at the airfoil as the function to be determined. It is shown how by integration by parts this integral equation can be transformed into the Biot-Savart theorem. A clarification is gained regarding the use of principal value definitions for the integral which occur. The integral equation of lifting-surface theory is used a s the starting point for the establishment of a theory for the nonstationary airfoil which is a generalization of lifting-line theory for the stationary airfoil and which might be called "lifting-strip" theory. Explicit expressions are given for section lift and section moment in terms of the circulation function, which for any given wing deflection is to be determined from an integral equation which is of the type of the equation of lifting-line theory. The results obtained are for airfoils of uniform chord. They can be extended to tapered airfoils. One of the main uses of the results should ...
Contributing Partner: UNT Libraries Government Documents Department
On the Instability of Methods for the Integration of Ordinary Differential Equations

On the Instability of Methods for the Integration of Ordinary Differential Equations

Date: April 1, 1956
Creator: Rutishauser, Heinz
Description: Examples and a criterion for stability of integration methods is provided. The criterion is applied to well-known integration formulas.
Contributing Partner: UNT Libraries Government Documents Department
On the Installation of Jet Engine Nacelles on a Wing Fourth Partial Report: Pressure-Distribution Measurements on a Sweptback Wing with Jet Engine Nacelle

On the Installation of Jet Engine Nacelles on a Wing Fourth Partial Report: Pressure-Distribution Measurements on a Sweptback Wing with Jet Engine Nacelle

Date: July 1, 1949
Creator: Buschner, R.
Description: The present report, which deals with pressure-distribution measurements made on a sweptback wing with a jet engine nacelle, is similar to a report on pressure-distribution measurements on a rectangular wing with a jet engine nacelle (second partial report). Here, in investigations preliminary to high-speed measurements, as in the second partial report, useful arrangements and fillet designs have been discovered.
Contributing Partner: UNT Libraries Government Documents Department